Large Angle Super Agile Attitude Maneuver Control of Small Satellite using Reaction Wheels

Based on multi-objective generic algorithms, a novel approach to optimizing control parameters for large angle spacecraft attitude was proposed. The large angle attitude maneuver controller was designed by taking the spacecraft nonlinear dynamics model and Lyapunov method. To optimize the controller parameters, the alterable weight coefficient method was adopted. Optimal value of time and power consumption acted as fitness goals of the algorithm. Simulation results showed that the algorithm proposed in this paper was superior to the traditional single-objective optimization design method.

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Large angle attitude maneuver control for rigid spacecraft with delayed inputs and disturbances

2015 23rd Iranian Conference on Electrical Engineering ◽

10.1109/iraniancee.2015.7146340 ◽

2015 ◽

Cited By ~ 1

Author(s):

Alireza Safa ◽

Mehdi Baradaran-nia ◽

Hamed Kharrati ◽

Sohrab Khanmohammadi

Keyword(s):

Large Angle ◽

Attitude Maneuver ◽

Rigid Spacecraft

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Attitude Active Disturbance Rejection Control of Agile Satellite

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.419.673 ◽

2013 ◽

Vol 419 ◽

pp. 673-681

Author(s):

Xiao Xiao Cai ◽

Jin Jie Wu ◽

Kun Liu

Keyword(s):

Disturbance Rejection ◽

Control Method ◽

Large Angle ◽

Control Moment ◽

Active Disturbance Rejection ◽

Disturbance Rejection Control ◽

Attitude Maneuver ◽

Agile Satellite ◽

Nonlinear Extended State Observer ◽

Pseudo Spectral Method

Based on the mission requirements of agile satellite, the control method of large angle maneuver was investigated in this paper. The single gimbal control moment gyroscope (sgcmg) of pyramid configuration is taken as the executor of the satellite. In order to avoid the singularity of sgcmgs, robust pseudo-inverse steering logic is used. An attitude active disturbance rejection controller (adrc) was designed. The expected attitude maneuver information that got by gauss pseudo-spectral method (gpm) took the place of that got by tracking differentiator (td). The constraints of satellite and sgcmgs are considered. Dynamics decoupling and disturbance observation of satellite were realized by using nonlinear extended state observer (neso). Then based on neso, nonlinear error feedback controller (nlsef) effectively suppresses the disturbance. The simulation results show that the attitude active disturbance rejection controller has steady control performance and can reject the disturbance better.

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Roll Attitude Maneuver of CMG-Based Controlled Small Satellite with Magnetic Torque Gimbal Angle Compensation System

SpaceOps 2016 Conference ◽

10.2514/6.2016-2602 ◽

2016 ◽

Author(s):

Mohd Badrul Salleh ◽

Nurulasikin Mohd Suhadis

Keyword(s):

Compensation System ◽

Small Satellite ◽

Magnetic Torque ◽

Attitude Maneuver

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Finite-Time Controller for Flexible Satellite Attitude Fast and Large-Angle Maneuver

Symmetry ◽

10.3390/sym14010045 ◽

2021 ◽

Vol 14 (1) ◽

pp. 45

Author(s):

You Li ◽

Haizhao Liang ◽

Lei Xing

Keyword(s):

Finite Time ◽

Sliding Mode ◽

Large Angle ◽

System Stability ◽

Satellite Attitude ◽

Attitude Maneuver ◽

Mode Parameter ◽

Mode Method ◽

Dynamic Sliding Mode ◽

Flexible Appendages

In order to deal with the fast, large-angle attitude maneuver with flexible appendages, a finite-time attitude controller is proposed in this paper. The finite-time sliding mode is constructed by implementing the dynamic sliding mode method; the sliding mode parameter is constructed to be time-varying; hence, the system could have a better convergence rate. The updated law of the sliding mode parameter is designed, and the performance of the standard sliding mode is largely improved; meanwhile, the inherent robustness could be maintained. In order to ensure the system’s state could converge along the proposed sliding mode, a finite-time controller is designed, and an auxiliary term is designed to deal with the torque caused by flexible vibration; hence, the vibration caused by flexible appendages could be suppressed. System stability is analyzed by the Lyapunov method, and the superiority of the proposed controller is demonstrated by numerical simulation.

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